CN106741930A - A kind of double differectial active speed regulating structure of multi-rotor aerocraft - Google Patents
A kind of double differectial active speed regulating structure of multi-rotor aerocraft Download PDFInfo
- Publication number
- CN106741930A CN106741930A CN201710083356.XA CN201710083356A CN106741930A CN 106741930 A CN106741930 A CN 106741930A CN 201710083356 A CN201710083356 A CN 201710083356A CN 106741930 A CN106741930 A CN 106741930A
- Authority
- CN
- China
- Prior art keywords
- main
- semiaxis
- differential mechanism
- conical tooth
- connection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/80—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement for differential adjustment of blade pitch between two or more lifting rotors
Abstract
The invention discloses a kind of double differectial active speed regulating structure of multi-rotor aerocraft, including frame shell and double differectial；The double differectial is made up of the first differential mechanism, the second differential mechanism and main distributor；The frame shell includes three chambers arranged in parallel；Main distributor is arranged in intermediate cavity；Differential mechanism is respectively symmetrically and is arranged in two side cavities；Main distributor is connected with both sides differential axle；Main distributor input is connected with main power shaft, and output end is connected with the main semiaxis in both sides；The output end of the main semiaxis in both sides is connected with differential axle respectively；The output end of the differential mechanism is connected with the propeller drive of aircraft；Also include an active arrangements for speed regulation；The active arrangements for speed regulation include a pinion frame, and at least two symmetrical planet conical tooths are provided with inside the pinion frame.
Description
Technical field
The present invention relates to vehicle technology field, the double differectial active speed governing knot of specially a kind of multi-rotor aerocraft
Structure.
Background technology
The electronic multi-rotor aerocraft of tradition, the every motor of branch shaft end is all independent driving, can be adjusted by each electricity and divided
Tiao Zheng correspondence motor rotating speed, using each motor institute, the pulling force difference of the speed difference generation with rotor adjusts the appearance of aircraft
State.The electronic many rotors of tradition are each independent speed governing of branch spindle motor, and the contact without mechanical aspects each other, simple structure is adjusted
But the means for saving attitude are single, usually out of question for self-contained power driving, but if using other high-powers react
Slow power source（For example engine etc.）The multi-rotor aerocraft of the single power dispersion this new structure of output of composition,
The need for adjustment attitude cannot just be met.
The need for the motor of the electronic multi-rotor aerocraft of tradition must simultaneously meet active force driving and pose adjustment,
Power utilization efficiency is low, it is impossible to always work in optimum state.
There is no good solution to this innovative multi-rotor aerocraft pose adjustment under prior art, not only very
The feature of aircraft is defined in big degree, and very big use obstacle is caused to user, limit whole many rotors
The fast development of aircraft industry.
The content of the invention
It is above-mentioned to solve it is an object of the invention to provide a kind of double differectial active speed regulating structure of multi-rotor aerocraft
The problem proposed in background technology.
To achieve the above object, the present invention provides following technical scheme：A kind of double differectial of multi-rotor aerocraft is actively
Speed regulating structure, including frame shell and double differectial；The double differectial is filled by the first differential mechanism, the second differential mechanism and main distribution
Put composition；The frame shell includes three chambers arranged in parallel；Main distributor is arranged in intermediate cavity；Differential mechanism point
It is not arranged symmetrically in two side cavities；Main distributor is connected with both sides differential axle；Main distributor input and active force
Axle is connected, and output end is connected with the main semiaxis in both sides；The output end of the main semiaxis in both sides is connected with differential axle respectively；The differential mechanism
Output end be connected with the propeller drive of aircraft；Also include an active arrangements for speed regulation；The active arrangements for speed regulation bag
A pinion frame is included, at least two symmetrical planet conical tooths are installed inside the pinion frame, main semiaxis connection
Main semiaxis conical tooth and from semiaxis connection from semiaxis conical tooth respectively the left and right sides by gear engage connect two planets
Conical tooth；The pinion frame periphery spur gear of the both sides engages connection auxiliary adjustment spur gear by gear.
Wherein, the main distributor includes the upper center main conical tooth, the middle part that are connected with main power shaft respectively with two
Side main semiaxis connection from conical tooth；Main conical tooth engages connection from conical tooth by gear.
Wherein, the frame shell is that integrated formed structure or three separate chambers cooperations are formed.
Compared with prior art, the beneficial effects of the invention are as follows：The present invention is rational in infrastructure, and feature is strong, and auxiliary power is just
Reversion change drives two pinion frame rotating Vortexes of double differectial, adjustment double differectial both sides by active arrangements for speed regulation
From the rotating speed inverse change of semiaxis, make the revolution speed of propeller on the both sides fulcrum of equispeed output that inverse change, i.e. side to occur and add
Other side is slowed down while fast, and then realizes changing the purpose of side revolution speed of propeller difference；The effect of active speed governing, two can be reached
Side propeller is connected by mechanical structure, is interacted, economical and practical, and durability is strong, and the present invention is total by rational structure,
By changing the speed discrepancy of each propeller in real time respectively, the attitude of aircraft can be dynamically adjusted in flight course, increased
The attitude regulation means of aircraft, greatly enhance the overall function of aircraft, are the various new many rotations of exploitation
Rotor aircraft provides more choices space, is particularly suitable for various single powers dispersion outputs, and be equipped with the low sound of high-power
Many rotors in speed power source are answered, the need for meeting its pose adjustment.For user provides great convenience.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is double differectial structural representation.
In Fig. 1-2：1. frame shell, 2. the first differential mechanism, 2 ' second differential mechanisms, 4. main distributor, 5. it is auxiliary distribution dress
Put, 10. propeller, 11. main conical tooths, 12. from conical tooth, 13. auxiliary conical tooths, 14. it is auxiliary from conical tooth, 15. planet conical tooths,
16. main semiaxis conical tooths, 17. from semiaxis conical tooth, 18. spline conical tooths, 19. rotating shaft conical teeth, 24. shaft couplings, 29. actively
Arrangements for speed regulation, 31. pinion frames, 32. auxiliary adjustment spur gears, 41. main power shafts, 42. auxiliary line shafts, 44. auxiliary output shafts,
45. from semiaxis, 47. ball spline shafts, 48. propeller rotating shafts, 52. shaft end hold-down supports, 55. spline housing L-type fixed seats, 56.
Shaft seat, 61. bearings, 82. spline housings.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
Fig. 1-2 is referred to, the present invention provides a kind of technical scheme：A kind of double differectial active speed governing of multi-rotor aerocraft
Structure, including frame shell 1 and double differectial；The double differectial is by the first differential mechanism 2, the second differential mechanism 2 ' and main distribution dress
Put 4 compositions；The frame shell 1 includes three chambers arranged in parallel；Main distributor 4 is arranged in intermediate cavity；Differential
Device 2,2 ' is respectively symmetrically and is arranged in two side cavities；Main distributor 4 is connected with the axle of both sides differential mechanism 2,2 '；Main distributor 4
Input is connected with main power shaft 41, output end and the main semiaxis in both sides（It is not shown）Connection；The output end difference of the main semiaxis in both sides
Connected with the axle of differential mechanism 2,2 '；The output end of the differential mechanism 2,2 ' is connected with the propeller drive of aircraft；Also include
One active arrangements for speed regulation 29；The active arrangements for speed regulation 29 include a pinion frame 31, the inside of the pinion frame 31 peace
Equipped with least two symmetrical planet conical tooths 15, the main semiaxis conical tooth 16 of main semiaxis connection and from the connection of semiaxis 45 from partly
Axle conical tooth 17 engages two planet conical tooths 15 of connection in the left and right sides by gear respectively；The pinion frame of the both sides
31 periphery spur gears engage connection auxiliary adjustment spur gear 32 by gear.The propeller drive of propeller 10 passes through
Shaft coupling 24 is connected with double differectial from semiaxis 45；Preferably, shaft coupling 24 is spline coupling.
Preferably, the main distributor 4 includes main conical tooth 11, the middle part that upper center is connected with main power shaft 41
Be not connected with the main semiaxis in both sides from conical tooth 12；Main conical tooth 11 engages connection from conical tooth 12 by gear.
Preferably, the frame shell 1 is that integrated formed structure or three separate chambers cooperations are formed.
Preferably, also including an auxiliary distributor 5；The auxiliary distributor 5 includes that lower end middle part connects with auxiliary line shaft 42
It is auxiliary from conical tooth 14 that the auxiliary conical tooth 13 that connects, a middle side part are connected with auxiliary output shaft 44；Auxiliary conical tooth 13 is engaged by gear
Connection is auxiliary from conical tooth 14.
Preferably, the propeller drive by shaft end hold-down support 52, deflecting conical tooth group, propeller rotating shaft 48,
Ball spline shaft 47, shaft end hold-down support 52, spline housing L-type fixed seat 55, shaft seat 56 and bearing 61 etc. are constituted.
Preferably, the deflecting conical tooth group includes the spline conical tooth 18 and top and propeller that are connected with spline housing 82
The rotating shaft conical tooth 19 of the connection of rotating shaft 48, spline conical tooth 18 engages connection rotating shaft conical tooth 19 by gear.
Preferably, the main conical tooth 11, from conical tooth 12, auxiliary conical tooth 13, auxiliary from conical tooth 14, planet conical tooth
15th, main semiaxis conical tooth 16, from the specification of semiaxis conical tooth 17, spline conical tooth 18 and rotating shaft conical tooth 19 at least one.
Preferably, the frame shell 1 and main power shaft 41, main semiaxis, auxiliary line shaft 42, auxiliary output shaft 44 with from semiaxis
45 junctions are equipped with bearing 61.
Preferably, the planet conical tooth 15 is equipped with bearing 61 with the junction of pinion frame 31.
Preferably, the shaft seat 56 is provided with bearing 61 with the junction of propeller rotating shaft 48.
Preferably, the shaft end hold-down support 52 is equipped with bearing 61 with the junction of splined shaft 47.
Preferably, the main power shaft 41, auxiliary line shaft 42, main semiaxis, auxiliary output shaft 44, turn from semiaxis 45 and propeller
The diameter specifications of axle 48 at least one.
Preferably, the diameter specifications of the periphery spur gear of the pinion frame 31 and auxiliary adjustment spur gear 32 are many
In one kind.
Preferably, the planet conical tooth 15 is no less than two.
Operation principle of the invention is：Symmetrically arranged first differential mechanism 2 in the left and right sides and the second differential mechanism 2 ' constitute double
Differential mechanism, the rotating change of auxiliary power drives two pinion frames 31 of double differectial in the same direction by active arrangements for speed regulation 29
Rotation, adjusts rotating speed inverse change of the double differectial both sides from semiaxis 45, makes the propeller 10 on the both sides fulcrum of equispeed output
There is other side while inverse change, i.e. side accelerate and slow down in rotating speed, make each propeller 10 of aircraft in flight course
In can realize relative rotation speed difference operation；Economical and practical, durability is strong.
By using cooperatively for multigroup bearing 61, can not only be improved integrally-built stability and practicality,
And substantial amounts of operating noise can be avoided the occurrence of, practicality is very strong.
The present invention is connected by rational structure design, both sides propeller by mechanical structure, is interacted, can be light
Easily change the speed discrepancy between each propeller, by changing the speed discrepancy of each propeller in real time respectively, largely
The overall function of aircraft is improve, the attitude regulation means of aircraft are increased.
The present invention is rational in infrastructure, practical, by active force driving device and auxiliary power drive device for adjusting posture phase
To separating and the technological means realized respectively, provided more choices space to develop various new multi-rotor aerocrafts, it is special
It is not suitable for various single power dispersions to export, and is equipped with many rotors in high-power low-response speed power source, meets its attitude
The need for adjustment.For user provides great convenience, with very strong practicality.
Although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
Understanding can carry out various changes, modification, replacement to these embodiments without departing from the principles and spirit of the present invention
And modification, the scope of the present invention be defined by the appended.
Claims (3)
1. the double differectial active speed regulating structure of a kind of multi-rotor aerocraft, it is characterised in that：Including frame shell（1）And double difference
Fast device；The double differectial is by the first differential mechanism（2）, the second differential mechanism（2’）With main distributor（4）Composition；Outside the framework
Shell（1）Including three chambers arranged in parallel；Main distributor（4）It is arranged in intermediate cavity；Differential mechanism（2,2 '）It is right respectively
Title is arranged in two side cavities；Main distributor（4）With both sides differential mechanism（2,2 '）Axle is connected；Main distributor（4）Input
With main power shaft（41）Connection, output end is connected with the main semiaxis in both sides；The output end of the main semiaxis in both sides respectively with differential mechanism（2,
2’）Axle is connected；The differential mechanism（2,2 '）Output end be connected with the propeller drive of aircraft；Also include that one actively adjusts
Speed variator（29）；The active arrangements for speed regulation（29）Including a pinion frame（31）, the pinion frame（31）Inside peace
Equipped with least two symmetrical planet conical tooths（15）, the main semiaxis conical tooth of main semiaxis connection（16）With from semiaxis（45）Connection
From semiaxis conical tooth（17）Two planet conical tooths of connection are engaged by gear in the left and right sides respectively（15）；The both sides
Pinion frame（31）Periphery spur gear engages connection auxiliary adjustment spur gear by gear（32）.
2. the double differectial active speed regulating structure of multi-rotor aerocraft as claimed in claim 1, it is characterised in that：The master point
With device（4）Including upper center and main power shaft（41）The main conical tooth of connection（11）, middle part connects with the main semiaxis in both sides respectively
Connect from conical tooth（12）；Main conical tooth（11）Connection from conical tooth is engaged by gear（12）.
3. the double differectial active speed regulating structure of a kind of multi-rotor aerocraft according to claim 1, it is characterised in that：Institute
State frame shell（1）It is that integrated formed structure or three separate chambers cooperations are formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710083356.XA CN106741930A (en) | 2017-02-16 | 2017-02-16 | A kind of double differectial active speed regulating structure of multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710083356.XA CN106741930A (en) | 2017-02-16 | 2017-02-16 | A kind of double differectial active speed regulating structure of multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741930A true CN106741930A (en) | 2017-05-31 |
Family
ID=58957928
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710083356.XA Withdrawn CN106741930A (en) | 2017-02-16 | 2017-02-16 | A kind of double differectial active speed regulating structure of multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741930A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018384A (en) * | 2018-09-18 | 2018-12-18 | 江苏心源航空科技有限公司 | A kind of novel multi-rotor unmanned aerial vehicle power device |
| CN109356990A (en) * | 2018-10-31 | 2019-02-19 | 韶关市广控机械传动技术有限公司 | A kind of differential assembly of Double-gear input |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101101047A (en) * | 2007-08-06 | 2008-01-09 | 刘淮滨 | Constant-speed differential speed double-axis reverse output transmission method and device |
| CN103029835A (en) * | 2011-09-29 | 2013-04-10 | 尤洛考普特公司 | Hybrid aircraft having a rotary wing |
| RU2525353C1 (en) * | 2013-03-15 | 2014-08-10 | Открытое Акционерное Общество "Московский Вертолетный Завод Им. М.Л. Миля" | Rotorcraft adjustable transmission |
| CN104309802A (en) * | 2014-10-21 | 2015-01-28 | 深圳大学 | Fuel power quadrotor unmanned aerial vehicle |
| CN106090174A (en) * | 2016-08-18 | 2016-11-09 | 北京驹创鼎盛科技发展有限公司 | Power transmission |
| CN206485572U (en) * | 2017-02-16 | 2017-09-12 | 莆田市双普信息科技有限公司 | A kind of double differectial active speed regulating structure of multi-rotor aerocraft |
-
2017
- 2017-02-16 CN CN201710083356.XA patent/CN106741930A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101101047A (en) * | 2007-08-06 | 2008-01-09 | 刘淮滨 | Constant-speed differential speed double-axis reverse output transmission method and device |
| CN103029835A (en) * | 2011-09-29 | 2013-04-10 | 尤洛考普特公司 | Hybrid aircraft having a rotary wing |
| RU2525353C1 (en) * | 2013-03-15 | 2014-08-10 | Открытое Акционерное Общество "Московский Вертолетный Завод Им. М.Л. Миля" | Rotorcraft adjustable transmission |
| CN104309802A (en) * | 2014-10-21 | 2015-01-28 | 深圳大学 | Fuel power quadrotor unmanned aerial vehicle |
| CN106090174A (en) * | 2016-08-18 | 2016-11-09 | 北京驹创鼎盛科技发展有限公司 | Power transmission |
| CN206485572U (en) * | 2017-02-16 | 2017-09-12 | 莆田市双普信息科技有限公司 | A kind of double differectial active speed regulating structure of multi-rotor aerocraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018384A (en) * | 2018-09-18 | 2018-12-18 | 江苏心源航空科技有限公司 | A kind of novel multi-rotor unmanned aerial vehicle power device |
| CN109356990A (en) * | 2018-10-31 | 2019-02-19 | 韶关市广控机械传动技术有限公司 | A kind of differential assembly of Double-gear input |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206485572U (en) | A kind of double differectial active speed regulating structure of multi-rotor aerocraft | |
| US11401042B2 (en) | Vertical take-off and landing aircraft and transformation gear sets for same | |
| CN111452608B (en) | Hybrid power transmission and electric driving device based on compound planetary gear train | |
| CN110435883B (en) | Transmission system of parallel reverse double-rotor helicopter | |
| CN106741930A (en) | A kind of double differectial active speed regulating structure of multi-rotor aerocraft | |
| CN210661264U (en) | Mechanical hydraulic parallel transmission gearbox assembly for harvesting machine | |
| CN106956770A (en) | A kind of aircraft active differential mechanism speed adjusting gear | |
| CN205890525U (en) | Bi -motor power device and electric automobile are arranged to single file star | |
| CN207267532U (en) | A kind of aircraft active differential mechanism speed adjusting gear | |
| CN104309466A (en) | Birotor motor type hybrid power drive of tracked vehicle | |
| CN104776202A (en) | Power flow division type acceleration gearbox for 6-8MW semi-direct driving wind generation set | |
| CN108016626B (en) | Electromechanical compound transmission device for aircraft | |
| CN206446795U (en) | A kind of multi-rotor aerocraft it is adjusted and controlled | |
| CN113650488B (en) | Transmission system with double-motor power coupling function | |
| CN105757192B (en) | The cyclic train arrangements for speed regulation of synchronous band structure | |
| CN211943725U (en) | Bevel gear coaxial contra-rotating combined type dual-rotor helicopter transmission mechanism | |
| CN102312974B (en) | Double-output hydraulic power generation planetary speed increaser | |
| WO2020259518A1 (en) | Battery electric vehicle and electric drive power system therefor | |
| CN210364411U (en) | Novel aircraft transmission system | |
| CN207826574U (en) | Oil moves coaxial six rotor wing unmanned aerial vehicles transmission mechanism | |
| CN113958668A (en) | Three-mode hybrid power stepless speed change device for tracked vehicle | |
| CN1684342A (en) | Differential stepless speed changing motor | |
| CN208306355U (en) | A kind of serial mixed power bull-dozer differential running gear of single motor driving | |
| CN111268114B (en) | Bevel gear coaxial counter-rotating double-rotor transmission mechanism | |
| CN113022285B (en) | Torque converging type electromechanical compound transmission device for tracked vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170531 |